Effect of the Launch Canister’s Rear Cover Configuration on the Formation of Initial Shock Waves in the Canister

doi:10.12382/bgxb.2022.0066

Abstract

Abstract:

In order to address the problem of inadequate intensity of the shock wave within the launch canister during its working process, the numerical approach is combined with the dynamic mesh adaptation method to study the generation mechanism of the initial shock wave within the canister and the flow phenomena involved in the technique of cover opening by gas detonation shock waves. First, the experimental results are comparatively analyzed to verify the accuracy of the proposed numerical approach and the reliability of the dynamic mesh refinement or unrefinement of the characteristics of the flow field of interest, such as the shock wave front and contact discontinuity. On that basis, the flat rear cover (primitive design) is taken as an example to expound on the evolution mechanism of the shock wave within the canister, which helps deepen the understanding of the working mechanism behind this technique. Then, the impact of the dome-shaped rear cover on the formation of shock waves within the canister is analyzed. The research results indicate that compared with the flat rear cover, the dome-shaped one can change the angle of collision between the air flow and the side wall at the canister tail, thus slowing down the formation of the turbulence area at this position, which significantly increases the initial shock wave intensity within the canister and increases the peak overpressure exerted on the front cover by around 48%. The findings of this study is of theoretical significance and engineering value to the overall launch canister design.

Key words: launch canister, rear cover configuration, adaptive mesh refinement, fragile cove, shock wave

LIANG Xiaoyang, LU Chenyu, LE Guigao. Effect of the Launch Canister’s Rear Cover Configuration on the Formation of Initial Shock Waves in the Canister[J]. Acta Armamentarii, 2023, 44(5): 1277-1287.

Figures/Tables 14

Fig.1 Schematic diagram of structure and monitoring surface distribution of a launch canister model

Table 1 Position distribution of monitoring surfaces in launch canister

相对位置	监测面0 (S-0)	监测面1 (S-1)	监测面2 (S-2)	监测面3 (S-3)	监测面4 (S-4)	监测面5 (S-5)
L/m	0.0	0.967	2.849	4.731	6.143	7.368

Fig.2 Computational domain and boundary conditions

Fig.3 Curve of total pressure varying with time of rocket engine combustion chamber

Table 2 Thermodynamic parameters of rocket engine

参数	取值
燃烧室总压p₀/MPa	总压-时间曲线
燃烧室总温T₀/K	3400
出口温度T/K	2253
定压比热c_p/(J·kg^-1·K^-1)	3866
比热比γ	1.1601
出口质量流量/(kg·s^-1)	86.98
燃气分子量/(kg·kmol^-1)	20.52
动力黏性系数μ/(N·s·m^-2)	9.34×10^-5

Fig.4 Grid independence verification

Fig.5 2D mesh adaptation process and data structure

Fig.6 Flow field comparison between test results and calculated results

Fig.7 Comparison of test results with numerical results of pressure distribution on the plate

Fig.8 Dynamic mesh adaptation during jet development

Fig.9 Developing process of the shock wave in the launch canister at different times

Fig.10 Shock wave propagation in the launch canister and interaction with the front cover

Fig.11 Comparison of shock wave formation in the caniser with different cover configurations (Left is plate type, right is dome type)

Fig.12 Overpressure curves of each monitoring surface and the front cover of the launch canister

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